Patents by Inventor Gerald Alexander Pauley
Gerald Alexander Pauley has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 10738630Abstract: A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.Type: GrantFiled: February 19, 2018Date of Patent: August 11, 2020Assignee: General Electric CompanyInventors: Qiang Li, Nicholas Joseph Kray, Gerald Alexander Pauley, Ming Xie, Jorge Orlando Lamboy, Tod Winton Davis
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Patent number: 10605117Abstract: A gas turbine including a fan platform positioned between adjacent fan blades of a fan of the gas turbine engine is provided. The fan platform defines an outer surface that at least partially defines an inner flowpath boundary of the fan. Additionally, the fan platform includes at least two components attached to one another. At least one of the components of the fan platform defines an enclosed void. An insert is positioned within the enclosed void formed of a material defining a relatively low Young's modulus. The insert may prevent resin from filling the enclosed void during assembly/manufacture of the fan platform, while also reducing a weight of the fan platform and an amount of stress on the fan platform.Type: GrantFiled: October 8, 2015Date of Patent: March 31, 2020Assignee: General Electric CompanyInventors: Mingchao Wang, Gerald Alexander Pauley
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Publication number: 20190257210Abstract: A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.Type: ApplicationFiled: February 19, 2018Publication date: August 22, 2019Inventors: Qiang Li, Nicholas Joseph Kray, Gerald Alexander Pauley, Ming Xie, Jorge Orlando Lamboy, Tod Winton Davis
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Publication number: 20170101876Abstract: A gas turbine including a fan platform positioned between adjacent fan blades of a fan of the gas turbine engine is provided. The fan platform defines an outer surface that at least partially defines an inner flowpath boundary of the fan. Additionally, the fan platform includes at least two components attached to one another. At least one of the components of the fan platform defines an enclosed void. An insert is positioned within the enclosed void formed of a material defining a relatively low Young's modulus. The insert may prevent resin from filling the enclosed void during assembly/manufacture of the fan platform, while also reducing a weight of the fan platform and an amount of stress on the fan platform.Type: ApplicationFiled: October 8, 2015Publication date: April 13, 2017Inventors: Mingchao Wang, Gerald Alexander Pauley
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Publication number: 20170101878Abstract: A gas turbine engine including a component having a first and a second component that are attached or integrally formed with each other. The first and the second component define an enclosed void. An insert is positioned within the enclosed void which is formed of a material having a relatively low Young's modulus. The insert may prevent resin from filling the enclosed void during assembly/manufacture of the component, while also reducing a weight of the component and an amount of stress on the component. The component may be a fan platform positioned between a plurality of fan blades, an outlet guide vane, or another component of the gas turbine engine.Type: ApplicationFiled: July 19, 2016Publication date: April 13, 2017Inventors: Mingchao Wang, Gerald Alexander Pauley, Courtney James Tudor, Elzbieta Kryj-Kos, Weizeng Kong
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Patent number: 9399922Abstract: Described are a gas turbine engine fan blade platform, related rotor assembly and gas turbine engine, as well as a method of assembling the same. The platform has a forward portion proximal to an axis of rotation, an aft portion, and a transition portion between the forward and aft portions. The forward portion has a forward interface surface facing axially forward, the aft portion has an aft interface surface facing radially outward, and the transition portion has at least one mounting feature. For the method of assembly, an aft support is installed on a fan disk and booster spool assembly. A plurality of fan blades are installed into a fan disk, followed by installing a fan platform between adjacent blades and securing the mounting features to the disk, thereby filling the annulus of the fan disk. Finally, a forward support is installed on the fan disk.Type: GrantFiled: December 31, 2012Date of Patent: July 26, 2016Assignee: General Electric CompanyInventors: Jorge Orlando Lamboy, Matthew Glen Gann, Nicholas Joseph Kray, Gerald Alexander Pauley, Daniel Allen Wilkin, II, Ming Xie
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Patent number: 9239062Abstract: A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.Type: GrantFiled: September 10, 2012Date of Patent: January 19, 2016Assignee: General Electric CompanyInventors: Jorge Orlando Lamboy, Nicholas Joseph Kray, Gerald Alexander Pauley, Qiang Li, Daniel Allen Wilkin, II, Tod Winton Davis
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Publication number: 20140219805Abstract: A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.Type: ApplicationFiled: September 10, 2012Publication date: August 7, 2014Inventors: Jorge Orlando Lamboy, Nicholas Joseph Kray, Gerald Alexander Pauley, Qiang Li, Daniel Allen Wilkin, II, Tod Winton Davis
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Publication number: 20140186187Abstract: Described are a gas turbine engine fan blade platform, related rotor assembly and gas turbine engine, as well as a method of assembling the same. The platform has a forward portion proximal to an axis of rotation, an aft portion, and a transition portion between the forward and aft portions. The forward portion has a forward interface surface facing axially forward, the aft portion has an aft interface surface facing radially outward, and the transition portion has at least one mounting feature. For the method of assembly, an aft support is installed on a fan disk and booster spool assembly. A plurality of fan blades are installed into a fan disk, followed by installing a fan platform between adjacent blades and securing the mounting features to the disk, thereby filling the annulus of the fan disk. Finally, a forward support is installed on the fan disk.Type: ApplicationFiled: December 31, 2012Publication date: July 3, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Jorge Orlando Lamboy, Matthew Glen Gann, Nicholas Joseph Kray, Gerald Alexander Pauley, Daniel Allen Wilkin, II, Ming Xie
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Publication number: 20140064938Abstract: A case apparatus for a gas turbine engine includes an annular case having an interior surface with annular recess formed therein; and an annular bumper disposed in the recess, the bumper comprising a frangible material and having a low-friction contact surface, wherein the bumper is configured to permit elastic radial deflection in response to applied forces below a predetermined threshold.Type: ApplicationFiled: September 6, 2012Publication date: March 6, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Michael Edward Eriksen, Gerald Alexander Pauley, Daniel Thomas Scorse
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Patent number: 7094033Abstract: A method for assembling a fan platform for a gas turbine engine is provided. The method includes determining an area of vulnerability to impact and erosion damage across the platform, forming a sheet of cladding metal to substantially conform to a contour of the identified area of vulnerability of the platform, and bonding the cladding metal to the identified area of vulnerability.Type: GrantFiled: January 21, 2004Date of Patent: August 22, 2006Assignee: General Electric CompanyInventors: Gerald Alexander Pauley, Brian Paul Overbeck
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Patent number: 7008689Abstract: A composite article, for example a blading member of a gas turbine engine, comprising a plurality of stacked layers of in-plane reinforcing fibers bonded together with a matrix resin is provided with enhanced resistance to impact cracking, material loss and/or delamination through use of a plurality of spaced apart reinforcing pins disposed into the article at an angle to the stacked layers, in one form disposed in a selected article region generally to resist strain energy generated during operation of the region. In another form, enhanced resistance is provided through the combination of a matrix resin including properties comprising a tensile strain property of at least 5% and a K1c toughness of at least about 850 psiĀ·inch1/2, and a plurality of spaced apart reinforcing pins disposed into the article at an angle to the stacked layers.Type: GrantFiled: July 18, 2001Date of Patent: March 7, 2006Assignee: General Electric CompanyInventors: James Thomas Hawkins, Gerald Alexander Pauley
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Patent number: 6843928Abstract: A method for removing metal cladding adhered to an airfoil, such as a turbine blade, wherein the airfoil comprises a substrate and wherein at least a portion of the cladding is adhered to at least one surface of the substrate of the airfoil. In this method the cladding is treated with a chemical etchant of the metal that the cladding is made of for a period of time sufficient to remove at least the portion of the cladding adhered to the at least one surface of the substrate. The substrate is made of a material that is chemically resistant to the etchant.Type: GrantFiled: October 12, 2001Date of Patent: January 18, 2005Assignee: General Electric CompanyInventors: Larry Dean Cline, Gerald Alexander Pauley
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Publication number: 20030203179Abstract: A composite article, for example a blading member of a gas turbine engine, comprising a plurality of stacked layers of in-plane reinforcing fibers bonded together with a matrix resin is provided with enhanced resistance to impact cracking, material loss and/or delamination through use of a plurality of spaced apart reinforcing pins disposed into the article at an angle to the stacked layers, in one form disposed in a selected article region generally to resist strain energy generated during operation of the region. In another form, enhanced resistance is provided through the combination of a matrix resin including properties comprising a tensile strain property of at least 5% and a K1c toughness of at least about 850 psi·inch1/2, and a plurality of spaced apart reinforcing pins disposed into the article at an angle to the stacked layers.Type: ApplicationFiled: July 18, 2001Publication date: October 30, 2003Inventors: James Thomas Hawkins, Gerald Alexander Pauley
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Publication number: 20030071019Abstract: A method for removing metal cladding adhered to an airfoil, such as a turbine blade, wherein the airfoil comprises a substrate and wherein at least a portion of the cladding is adhered to at least one surface of the substrate of the airfoil. In this method the cladding is treated with a chemical etchant of the metal that the cladding is made of for a period of time sufficient to remove at least the portion of the cladding adhered to the at least one surface of the substrate. The substrate is made of a material that is chemically resistant to the etchant.Type: ApplicationFiled: October 12, 2001Publication date: April 17, 2003Inventors: Larry Dean Cline, Gerald Alexander Pauley
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Patent number: 6413051Abstract: An article including a body terminating in an end portion, for example an airfoil of a blade terminating in an airfoil tip, comprises an end or tip barrier discrete from and bonded with the body. The barrier is substantially impregnable to penetration of liquid, for example water vapor. In a form in which the body is laminated, the barrier is a non-directionally dependent material, resisting delamination. In one form of a method for making such article, the end portion of an existing article is trimmed back to provide a body preform, and an end barrier is bonded with the body preform. In another method form, an end barrier is bonded with a provided body preform, the barrier and body preform together defining the article. Such articles are repairable by removing and replacing a damaged end portion or damaged barrier.Type: GrantFiled: October 30, 2000Date of Patent: July 2, 2002Assignee: General Electric CompanyInventors: Chen-Yu Jack Chou, Gerald Alexander Pauley